U.S. patent application number 13/539627 was filed with the patent office on 2014-01-02 for airfoil for improved flow distribution with high radial offset.
The applicant listed for this patent is Noel Modesto-Madera, Thomas J. Praisner. Invention is credited to Noel Modesto-Madera, Thomas J. Praisner.
Application Number | 20140003925 13/539627 |
Document ID | / |
Family ID | 49778350 |
Filed Date | 2014-01-02 |
United States Patent
Application |
20140003925 |
Kind Code |
A1 |
Praisner; Thomas J. ; et
al. |
January 2, 2014 |
AIRFOIL FOR IMPROVED FLOW DISTRIBUTION WITH HIGH RADIAL OFFSET
Abstract
A vane assembly for use in a gas flow duct. The vane assembly
includes multiple vanes arranged circumferentially about the duct.
A throat angle of each of the vanes at mid-span is greater than the
throat angel at the tips of the vane.
Inventors: |
Praisner; Thomas J.;
(Colchester, CT) ; Modesto-Madera; Noel;
(Manchester, CT) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Praisner; Thomas J.
Modesto-Madera; Noel |
Colchester
Manchester |
CT
CT |
US
US |
|
|
Family ID: |
49778350 |
Appl. No.: |
13/539627 |
Filed: |
July 2, 2012 |
Current U.S.
Class: |
415/185 |
Current CPC
Class: |
F01D 5/12 20130101; Y02T
50/673 20130101; F01D 5/141 20130101; Y02T 50/60 20130101; F01D
9/041 20130101 |
Class at
Publication: |
415/185 |
International
Class: |
F01D 5/12 20060101
F01D005/12 |
Claims
1. A vane assembly for a duct comprising: a plurality of vanes
arranged circumferentially about an axis defined by a duct; wherein
each of said plurality of vanes has a throat distance defining a
shortest distance between the vane and an adjacent vane at a
constant span; wherein the throat distance defines a throat angle
relative to a line tangential to a trailing edge of each of said
plurality of vanes; and wherein the throat angle of each vane at
mid-span is greater than the throat angle at the tip region of each
vane.
2. The vane assembly of claim 1, wherein said stationary duct has a
duct angle of at least ten degrees, relative to the axis defined by
the stationary duct.
3. The vane assembly of claim 1, wherein each vane in said
plurality of vanes has an aspect ratio of less than or equal to
1.5.
4. The vane assembly of claim 1, wherein said plurality of vanes
includes an even number of vanes.
5. The vane assembly of claim 1, wherein said plurality of vanes
includes less than or equal to twenty vanes.
6. The vane assembly of claim 1, further comprising a root throat
angle at a root region of the vane, wherein the root throat angle
is less than the throat angle.
7. The vane assembly of claim 6, wherein the root throat angle is a
throat angle measured at less than or equal to 5% span of the
vane.
8. The vane assembly of claim 1, wherein the tip region throat
angle is a throat angle measured at greater than or equal to 95%
span of the vane.
9. The vane assembly of claim 1, wherein said mid-span throat angle
is a smallest throat angle in a range of throat angles between 5%
span and 95% span.
10. The vane assembly of claim 9, wherein said mid-span throat
angle is a smallest throat angle in a range of throat angles
between 45% span and 55% span.
11. The vane assembly of claim 1, wherein an airflow at an outer
diameter of said vane assembly is elevated relative to an airflow
at a mid-span region of the vane assembly.
12. The vane assembly of claim 11, wherein an airflow at an inner
diameter of said vane assembly is elevated relative to an airflow
at a mid-span region of the vane assembly.
13. A jet engine comprising: a gas path duct having a vane
assembly, wherein the vane assembly has a plurality of vanes
arranged circumferentially about an axis defined by the gas path
duct; wherein each of said plurality of vanes has a throat distance
defining a shortest distance between the vane and an adjacent vane
at a constant span; wherein the throat distance defines a throat
angle relative to a line tangential to a trailing edge of each of
said plurality of vanes; and wherein the throat angle of each vane
at mid-span is greater than the throat angle at the tip region of
each vane.
14. The jet engine of claim 12, wherein said gas path duct has a
duct angle of at least ten degrees, relative to the axis defined by
the gas path duct.
15. The jet engine of claim 13, wherein each of said plurality of
vanes has an aspect ratio of less than or equal to 1.5.
16. The jet engine of claim 12, wherein said plurality of vanes is
an even number of vanes.
17. The jet engine of claim 12, wherein said plurality of vanes is
less than or equal to twenty vanes.
18. The jet engine of claim 13, wherein said plurality of vanes
further define a root throat angle, wherein the root throat angle
is less than the mid-span throat angle.
19. The jet engine of claim 18 wherein the root throat angle is a
throat angle measured at less than or equal to 5% span of the
vane.
20. The jet engine of claim 12, wherein the tip region throat angle
is a throat angle measured at greater than or equal to 95% span of
the vane.
21. The jet engine of claim 12, wherein said mid-span throat angle
is a smallest throat angle in a range of throat angles between 5%
span and 95% span.
22. The jet engine of claim 21, wherein said mid-span throat angle
is a smallest throat angle in a range of throat angles between 45%
span and 55% span.
23. The jet engine of claim 13, wherein an airflow at an outer
diameter of said vane assembly is elevated relative to an airflow
at a mid-span region of the vane assembly.
24. The jet engine of claim 23, wherein an airflow at an inner
diameter of said vane assembly is elevated relative to an airflow
at the mid-span region of the vane assembly.
Description
TECHNICAL FIELD
[0001] The present disclosure is directed to stationary vane
assemblies for airflow ducts, and more particularly to a spanwise
throat angle distribution for the same.
BACKGROUND OF THE INVENTION
[0002] Mechanical systems incorporating airflow ducts, such as jet
engines, often include stationary vanes within the airflow ducts.
The stationary vanes control airflow through the duct and impart
desirable flow characteristics, such as turning, onto the airflow.
Known stationary (stator) vanes with a low aspect ratio are
typically included in ducts having a relatively long exit duct
portion after the trailing edge of the vane. As a result of the low
aspect ratio and the relatively long exit duct portion, flow
quality problems can arise at the inner diameter and the outer
diameter of the duct.
SUMMARY OF THE INVENTION
[0003] A vane assembly for a duct according to an exemplary
embodiment of this disclosure, among other possible things includes
a plurality of vanes arranged circumferentially about an axis
defined by a duct, each of said plurality of vanes has a throat
distance defining a shortest distance between the vane and an
adjacent vane at a constant span, the throat distance defines a
throat angle relative to a line tangential to a trailing edge of
each of said plurality of vanes, and the throat angle of each vane
at mid-span is greater than the throat angle at the tip region of
each vane.
[0004] In a further embodiment of the foregoing vane assembly, the
stationary duct has a duct angle of at least ten degrees, relative
to the axis defined by the stationary duct.
[0005] In a further embodiment of any of the foregoing vane
assemblies, each vane in said plurality of vanes has an aspect
ratio of less than or equal to 1.5.
[0006] In a further embodiment of any of the foregoing vane
assemblies, the plurality of vanes includes an even number of
vanes.
[0007] In a further embodiment of any of the foregoing vane
assemblies, the plurality of vanes includes less than or equal to
twenty vanes.
[0008] In a further embodiment of any of the foregoing vane
assemblies, further including a root throat angle at a root region
of the vane, wherein the root throat angle is less than the throat
angle.
[0009] In a further embodiment of any of the foregoing vane
assemblies, the root throat angle is a throat angle measured at
less than or equal to 5% span of the vane.
[0010] In a further embodiment of any of the foregoing vane
assemblies, the tip region throat angle is a throat angle measured
at greater than or equal to 95% span of the vane.
[0011] In a further embodiment of any of the foregoing vane
assemblies, the mid-span throat angle is a smallest throat angle in
a range of throat angles between 5% span and 95% span.
[0012] In a further embodiment of any of the foregoing vane
assemblies, the mid-span throat angle is a smallest throat angle in
a range of throat angles between 45% span and 55% span.
[0013] In a further embodiment of any of the foregoing vane
assemblies, an airflow at an outer diameter of said vane assembly
is elevated relative to an airflow at a mid-span region of the vane
assembly.
[0014] In a further embodiment of any of the foregoing vane
assemblies, an airflow at an inner diameter of said vane assembly
is elevated relative to an airflow at a mid-span region of the vane
assembly.
[0015] A jet engine according to an exemplary embodiment of this
disclosure, among other possible things includes a gas path duct
having a vane assembly. The vane assembly has a plurality of vanes
arranged circumferentially about an axis defined by the gas path
duct. Each of said plurality of vanes has a throat distance
defining a shortest distance between the vane and an adjacent vane
at a constant span. The throat distance defines a throat angle
relative to a line tangential to a trailing edge of each of said
plurality of vanes. The throat angle of each vane at mid-span is
greater than the throat angle at the tip region of each vane.
[0016] In a further embodiment of the foregoing jet engine, the gas
path duct has a duct angle of at least ten degrees, relative to the
axis defined by the gas path duct.
[0017] In a further embodiment of any of the foregoing jet engines,
each of said plurality of vanes has an aspect ratio of less than or
equal to 1.5.
[0018] In a further embodiment of any of the foregoing jet engines,
the plurality of vanes is an even number of vanes.
[0019] In a further embodiment of any of the foregoing jet engines,
the plurality of vanes is less than or equal to twenty vanes.
[0020] In a further embodiment of any of the foregoing jet engines,
the plurality of vanes further define a root throat angle, wherein
the root throat angle is less than the mid-span throat angle.
[0021] In a further embodiment of any of the foregoing jet engines,
the root throat angle is a throat angle measured at less than or
equal to 5% span of the vane.
[0022] In a further embodiment of any of the foregoing jet engines,
the tip region throat angle is a throat angle measured at greater
than or equal to 95% span of the vane.
[0023] In a further embodiment of any of the foregoing jet engines,
the mid-span throat angle is a smallest throat angle in a range of
throat angles between 5% span and 95% span.
[0024] In a further embodiment of any of the foregoing jet engines,
the mid-span throat angle is a smallest throat angle in a range of
throat angles between 45% span and 55% span.
[0025] In a further embodiment of any of the foregoing jet engines,
an airflow at an outer diameter of said vane assembly is elevated
relative to an airflow at a mid-span region of the vane
assembly.
[0026] In a further embodiment of any of the foregoing jet engines,
an airflow at an inner diameter of said vane assembly is elevated
relative to an airflow at the mid-span region of the vane
assembly.
[0027] These and other features of the present invention can be
best understood from the following specification and drawings, the
following of which is a brief description.
BRIEF DESCRIPTION OF THE DRAWINGS
[0028] FIG. 1 illustrates a side view of a single stationary vane
of a vane assembly in an airflow duct.
[0029] FIG. 2 illustrates a top (tip) view of two stationary vanes
in the stationary vane assembly of FIG. 1.
[0030] FIG. 3a illustrates an outer diameter layer of a vane in one
example vane assembly arrangement.
[0031] FIG. 3b illustrates a top view of a mid-span layer of the
example vane assembly arrangement of FIG. 3a.
[0032] FIG. 4 illustrates a top view of a root layer of an optional
feature of the example vane assembly arrangement of FIG. 3a.
[0033] FIG. 5 illustrates a chart showing a progression of throat
angles related to percent span of the example arrangement of FIGS.
3a, 3b and 4.
DETAILED DESCRIPTION
[0034] FIG. 1 illustrates a stationary vane assembly 10 in a duct
20. The duct 20 is a circular duct and defines an axis A running
through the center of the duct 20. The vane assembly 10 includes
multiple individual vanes 12 arranged circumferentially about the
axis A. In one example, the vanes 12 are substantially identical,
and are equidistantly spaced about the vane assembly 10. In one
example, there are less than or equal to 20 vanes. In an alternate
example there is an even number of vanes. The duct 20 has a duct
angle 70 defined as the angle of a mid-span line 72 of the vane 12
relative to the axis A defined by the duct 20. The mid-span line 72
is drawn along the vane 12 at 50% span. An airflow 30 through the
duct 20 is shown including arrows illustrating the direction of the
airflow 30. The airflow 30 encounters a leading edge 40 of the vane
12 and is forced around the vane 12. The leading edge 40 has a span
42 extending from an inner diameter wall 62 of the duct 20 (0%
span) to an outer diameter wall 64 of the duct 20 (100% span).
Downstream of the leading edge 40, the airflow 30 encounters a
trailing edge 50 of the vane 12 as the airflow 30 passes the vane
12. The trailing edge 50 of the vane 12 has a trailing edge span 52
extending from the inner diameter wall 62 (0% span) to the outer
diameter wall 64 (100% span). The axial length of the vane 12 is
referred to as the axial chord length 60.
[0035] Each vane 12 is in the vane assembly 10 has an aspect ratio
that defines features of the vane. The aspect ratio is dependent on
the length 42 of leading edge 40 span, the length of the trailing
edge 50 span 52, and the length of the axial chord and is defined
as being: Aspect Ratio=(leading edge span 42+trailing edge span
52)/(2*axial chord 60). In the illustrated example, the aspect
ratio is approximately 1.5. In alternate examples, the aspect ratio
is less than 1.5.
[0036] Due to the circumferential vane 12 arrangement of the vane
assembly 10, the features of each vane 12 define a throat distance
between each vane 12 and each adjacent vane 12 at any given span of
the vanes 12. The throat distance is the shortest single span
distance from one vane 12 to an adjacent vane 12 in the vane
assembly 10. The throat distance, as well as the throat angle,
varies depending on the span. Thus, the throat distance and the
throat angles of the vane assembly 10 will vary depending on what
span percentage is being measured.
[0037] FIG. 2 illustrates a top view of two vanes 110 in the
stationary vane assembly 10 illustrated in FIG. 1. Each of the
vanes 110 has a leading edge 140 that initially contacts the
airflow 30 (illustrated in FIG. 1). As the airflow 30 passes over
the vanes 110 in the vane assembly 10, the contours of each
individual vane 110 generate a pressure differential between the
two sides of the vane 110. In the illustrated example vanes 110,
the top side is a pressure side 112 and the bottom side of the
vanes 110 is a suction side 114. The airflow immediately adjacent
the suction side 112 has a pressure that is lower than the airflow
immediately adjacent the pressure side 114.
[0038] As described above, the smallest distance between the two
adjacent vanes 110, at a constant span percentage, is the throat
distance 180. The throat distance at any given span percentage is
uniquely defined by a single point on the suction side 112 of one
vane 110 and a corresponding single point on the pressure side 114
of an adjacent vane 110. A line drawn along the throat distance 180
defines a throat angle 190 relative to a circumferential line 192
that is tangential to the trailing edge 150 of each of the vanes
110 within the vane assembly 10.
[0039] FIGS. 3a and 3b illustrate an outer diameter layer of a vane
210 at a span of 95-100% (FIG. 3a) and a mid-span layer of the vane
210 at a span of 45-55% (FIG. 3b). The tip, or 95-100% span region,
is at the outer diameter endwall 64 of the duct 20. As with FIG. 2,
each of the illustrated vanes 210 includes a leading edge 240, a
pressure side 212, a suction side 214, and a trailing edge 250. The
throat distance 280 at the mid-span (FIG. 3b) is shorter than the
throat distance 280 at the tip (95-100% span). Similarly, the
pressure side point defining the throat distance at the tip on each
vane 210 is axially downstream from the pressure side point
defining the throat distance 280 at mid-span on each vane 210.
Because of this relationship, the throat angle 290 at mid-span is
larger than the throat angle 290 at the tip, and airflow angle at
the tip is opened up relative to airflow at mid-span.
[0040] FIG. 4 illustrates an optional feature of the root portion
(0-5% span) of the vanes 210 that can be included in the vane
assembly illustrated in FIGS. 3a and 3b. The root, or 0-5% span
region of the vane 210, is at the inner diameter endwall 62 of the
duct 20. In the optional feature, the pressure side point defining
the throat distance 280 at the root (0-5% span) of the vane 210 is
downstream of the pressure side point defining the throat distance
280 at mid-span (45-55% span). As a result of this feature, the
throat angle 290 at mid-span of the vane 210 in the example of
FIGS. 3a, 3b and 4 is larger than the throat angle 290 at either
the tip (95-100% span) or the root (0-5% span), and the airflow at
the outer diameter and the inner diameter is opened up relative to
airflow at mid-span.
[0041] FIG. 5 illustrates a chart showing the throat angles, with
respect to percent span, of the example vane of FIG. 3a, 3b without
the inclusion of the feature of FIG. 4 as line 410 and with the
inclusion of the feature of FIG. 4 as line 420. As can be seen by
line 410, in the example not including the optional feature of FIG.
4 the throat angle has a small decline as the percent span of the
vane increases from 0% span 412 (the root of the vane) to mid-span
414, and then sharply declines from mid-span 414 to 100% span 416
(the tip of the vane). In the line 422, for the example where the
optional feature of FIG. 4 included, the throat angle starts with a
low throat angle at 0% span 422 (the root of the vane) and
increases until it reaches mid-span 424 (45-55% span), where the
throat angle begins decreasing again until 100% span 426 (the
tip).
[0042] In the example of FIG. 4, the vanes 110, 210 are designed
with relatively open throat angles near the root (inner diameter
wall) and tip (outer diameter wall) and a relatively closed throat
angle near the mid-span of the vane. By utilizing this varied
throat angle configuration, the airflow along the end walls is
increased relative to the flows at the mid-span line (where the
throat angle is minimized). This airflow vortexing achieves a
better flow distribution including more flow to the end wall
regions of the duct 20. In one example implementation, the above
described features are included in a vane assembly in a gas path of
a jet engine.
[0043] Although a embodiment of this invention has been disclosed,
a worker of ordinary skill in this art would recognize that certain
modifications would come within the scope of this invention. For
that reason, the following claims should be studied to determine
the true scope and content of this invention.
* * * * *